Advancement of Small Gas Turbine Component Technology, Advanced Small Axial Compressor. Volume 1. Analysis and Design. Addendum

Abstract

A complete two-stage aerodynamic axial compressor design capable of being matched with the USAAVLABS advanced centrifugal technology was prepared. Fully variable part span inlet guide vanes were designed. Two transition ducts were also designed to provide an efficient aerodynamic flow path from the axial compressor exit to the centrifugal compressor inlet.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1969
Accession Number
AD0506812

Entities

People

  • James V. Davis

Tags

Communities of Interest

  • Air Platforms
  • Human Systems

DTIC Thesaurus Topics

  • Army Aviation
  • Centrifugal Compressors
  • Compressors
  • Contracts
  • Engineering
  • Gas Turbines
  • Geometry
  • Governments
  • Guide Vanes
  • Inlet Guide Vanes
  • Inlets
  • Mach Number
  • Security
  • Turbine Components
  • Turbines
  • United States
  • Virginia

Fields of Study

  • Engineering

Readers

  • Aerodynamics.
  • Software Engineering